IN2014DN08528A - - Google Patents

Download PDF

Info

Publication number
IN2014DN08528A
IN2014DN08528A IN8528DEN2014A IN2014DN08528A IN 2014DN08528 A IN2014DN08528 A IN 2014DN08528A IN 8528DEN2014 A IN8528DEN2014 A IN 8528DEN2014A IN 2014DN08528 A IN2014DN08528 A IN 2014DN08528A
Authority
IN
India
Prior art keywords
shell ring
holes
portions
dilution holes
platelets
Prior art date
Application number
Inventor
Denis Jean Maurice Sandelis
Original Assignee
Snecma
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Snecma filed Critical Snecma
Publication of IN2014DN08528A publication Critical patent/IN2014DN08528A/en

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03041—Effusion cooled combustion chamber walls or domes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03042—Film cooled combustion chamber walls or domes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)

Abstract

The dilution holes (39) in a shell ring (2,3) of a turbomachine combustion chamber are covered with platelets (40) which delimit chambers (49) around them on the interior face of the shell ring. Ventilation holes (45) passing through the platelet cause those portions of the shell ring surrounding the dilution holes (39) to be ventilated cooling these portions and preventing crack formation.
IN8528DEN2014 2012-05-25 2013-05-23 IN2014DN08528A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1254847A FR2991028B1 (en) 2012-05-25 2012-05-25 TURBOMACHINE COMBUSTION CHAMBER VIROLE
PCT/FR2013/051117 WO2013175126A2 (en) 2012-05-25 2013-05-23 Turbomachine combustion chamber shell ring

Publications (1)

Publication Number Publication Date
IN2014DN08528A true IN2014DN08528A (en) 2015-05-15

Family

ID=46754628

Family Applications (1)

Application Number Title Priority Date Filing Date
IN8528DEN2014 IN2014DN08528A (en) 2012-05-25 2013-05-23

Country Status (9)

Country Link
US (1) US9377200B2 (en)
EP (1) EP2856036B1 (en)
CN (1) CN104520647B (en)
BR (1) BR112014027018B1 (en)
CA (1) CA2871923C (en)
FR (1) FR2991028B1 (en)
IN (1) IN2014DN08528A (en)
RU (1) RU2626876C2 (en)
WO (1) WO2013175126A2 (en)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102012022259A1 (en) * 2012-11-13 2014-05-28 Rolls-Royce Deutschland Ltd & Co Kg Combustor shingle of a gas turbine and process for its production
WO2015100346A1 (en) 2013-12-23 2015-07-02 United Technologies Corporation Multi-streamed dilution hole configuration for a gas turbine engine
US10451281B2 (en) * 2014-11-04 2019-10-22 United Technologies Corporation Low lump mass combustor wall with quench aperture(s)
US10386072B2 (en) * 2015-09-02 2019-08-20 Pratt & Whitney Canada Corp. Internally cooled dilution hole bosses for gas turbine engine combustors
US20180283689A1 (en) * 2017-04-03 2018-10-04 General Electric Company Film starters in combustors of gas turbine engines
US11187412B2 (en) 2018-08-22 2021-11-30 General Electric Company Flow control wall assembly for heat engine

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1052475A (en) * 1952-03-15 1954-01-25 Snecma Combustion chambers particularly suitable for gas turbines
GB777782A (en) 1955-06-24 1957-06-26 Ici Ltd Purification of terephthalic acid
US4132066A (en) * 1977-09-23 1979-01-02 United Technologies Corporation Combustor liner for gas turbine engine
US4875339A (en) * 1987-11-27 1989-10-24 General Electric Company Combustion chamber liner insert
US4887432A (en) * 1988-10-07 1989-12-19 Westinghouse Electric Corp. Gas turbine combustion chamber with air scoops
FR2855249B1 (en) * 2003-05-20 2005-07-08 Snecma Moteurs COMBUSTION CHAMBER HAVING A FLEXIBLE CONNECTION BETWEEN A BOTTOM BED AND A BEDROOM
RU2260748C2 (en) * 2003-12-02 2005-09-20 Открытое акционерное общество "Авиадвигатель" Combustion chamber for gas-turbine engine
FR2881813B1 (en) * 2005-02-09 2011-04-08 Snecma Moteurs TURBOMACHINE COMBUSTION CHAMBER FAIRING
FR2892180B1 (en) * 2005-10-18 2008-02-01 Snecma Sa IMPROVING THE PERFOMANCE OF A COMBUSTION CHAMBER BY MULTIPERFORATING THE WALLS
FR2899315B1 (en) 2006-03-30 2012-09-28 Snecma CONFIGURING DILUTION OPENINGS IN A TURBOMACHINE COMBUSTION CHAMBER WALL
US8171634B2 (en) * 2007-07-09 2012-05-08 Pratt & Whitney Canada Corp. Method of producing effusion holes
US8789372B2 (en) * 2009-07-08 2014-07-29 General Electric Company Injector with integrated resonator

Also Published As

Publication number Publication date
FR2991028A1 (en) 2013-11-29
RU2014152849A (en) 2016-07-20
EP2856036A2 (en) 2015-04-08
WO2013175126A2 (en) 2013-11-28
WO2013175126A3 (en) 2014-04-24
CN104520647B (en) 2016-02-24
FR2991028B1 (en) 2014-07-04
US9377200B2 (en) 2016-06-28
BR112014027018B1 (en) 2021-05-25
US20150059344A1 (en) 2015-03-05
CA2871923A1 (en) 2013-11-28
CA2871923C (en) 2020-02-11
RU2626876C2 (en) 2017-08-02
BR112014027018A2 (en) 2017-06-27
EP2856036B1 (en) 2018-09-12
CN104520647A (en) 2015-04-15

Similar Documents

Publication Publication Date Title
IN2014DN08528A (en)
EP2904238A4 (en) COOLING OF COMBUSTION CHAMBER SHIRTS WITH ACCELERATION CHANNELS
PL3128155T3 (en) Turboprop engine assembly with combined engine and cooling exhaust
GB2527714A (en) Flow conditioner and method of designing same
PL3135881T3 (en) Engine assembly with combined engine and cooling exhaust
CL2016003109A1 (en) A gas ventilation mask, comprising a nasal mask and a mouth mask, detachably connected to each other, in which nasal and oral chambers are connected to each other through an automatic closing partition or valve.
EP3019704A4 (en) Gas turbine engine component cooling with resupply of cooling passage
NZ718810A (en) Mask vent with side wall
WO2015147929A3 (en) Cooling an aperture body of a combustor wall
WO2014189589A3 (en) Gas turbine engine with soft mounted pre-swirl nozzle
WO2015112220A3 (en) Turbine engine combustor heat shield with one or more cooling elements
WO2015147938A3 (en) A cooled grommet for a combustor wall assembly
EP3108130A4 (en) Gas turbine engine having minimum cooling airflow
EP2859205A4 (en) COMBUSTION CHAMBER LINING WITH REDUCED COOLING DILUTION OPENINGS
EP3495617B8 (en) Airfoil with internal cooling passages
EP3039264A4 (en) Gas turbine engine diffuser cooling and mixing arrangement
GB201504677D0 (en) HPT Integrated interstage seal and cooling air passageways
BR112016010483A8 (en) bearing
MX2016001313A (en) Heat shield with standoffs.
EP3044418A4 (en) Gas turbine engine airfoil with wishbone baffle cooling scheme
FR2981132B1 (en) DISCHARGE COOLING TURBOMACHINE ASSEMBLY
EA201490225A1 (en) CANDLES CONTAINER WITH INTERNAL AIR CIRCULATION
GB2517029B (en) Turbine blade platform with radially inner and outer cooling cavities
WO2015004378A3 (en) Seal for an electrolyser cell and electrolyser cell provided with such a seal
EP3382156B8 (en) Gas turbine with cooled cooling air for blade air seal through outer chamber